SUBSTANCE: invention refers to modelling and can be applied for behaviour modelling for aviation structures and products with uncertain input parameters. Method involves behaviour modelling for aviation structures and products with uncertain input parameters at two levels: at macro level by method of end element modelling, and at micro level by quantum and molecular mechanics methods; first, microscopic samples of the model similar geometrically to standard samples used in mechanical tests are examined and tested by molecular dynamics methods, and obtained mechanical parameters of microscopic samples are used as missing macroscopic parameters in material models for end element modelling; transition from micro to macro level and back is made with the use of scale invariance of mechanical parameters and laws.

EFFECT: increased accuracy of mechanical and operation property tests of developed and reconstructed units and components.

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The invention relates to methods of mathematical and computer modeling to create a model of the behavior of structures and components of aircraft in conditions of uncertainty of input parameters.

The prior art method of mathematical modeling [1], which are used and compared methods finite element and molecular dynamics simulation. A significant disadvantage of the proposed method is that it addresses only limited modeling fracture and are not predicted properties of materials. In addition, this method does not allow to consider the issues of modeling with the uncertainty of resource product.

Known {2] the method of the hierarchical structural modeling, including the use of basic modeling elements and additional connecting elements, geometrically similar simulated, thus splitting at the elementary elements is used to simplify the computational model and is not associated with the uncertainty of the design parameters. The disadvantage of this method is the inability to obtain the unknown parameters in the simulation of aircraft, since the elements of the partition are assumed to be given and has known mechanical properties

Well-known computer mod is whether the behavior of complex technical systems,
implemented on different hierarchical levels [3]. The closest analogue, i.e. a prototype. According to the method for modeling the active zone of the nuclear reactor is introduced cellular structure of several hierarchical levels, the simulated parameters are considered at the level of the minimum cell and subsequently Srednyaya and used to estimate the behavior of a design at a higher scale level. The disadvantage of this method is that the use of the averaging procedure leads to the neglect of important, albeit single elements, for example, inclusions of foreign substances in the active zone. The presence of this kind of single inclusions can impair the functioning of the structure, to cause catastrophic consequences. In addition, the prototype does not take into account effects due to uncertainty of input parameters.

The essence of the problem is the modeling of the aircraft associated with the presence of two types of uncertainties. The first type is incomplete information on the properties of the materials used. Some of these data can be obtained from manufacturers, but the accuracy of the information questionable, which is unacceptable for the design of critical parts. These data can be obtained by conducting a bench test, but it is quite expensive, and Ino is even possible.
The second type of uncertainty is associated with the real stresses on the aircraft during operation. The study of the specific loading conditions and the resulting force factors in the design generally requires expensive experiments in wind tunnels or in test flights.

Problem which is solved by this invention is a method of multilevel computer simulations that allow a high degree of accuracy to virtually test the mechanical and operational properties of the developed and rebuilt units and parts at different scale levels, allowing the use of model materials and products that meet real.

This task is solved by the method of mathematical and computer modeling involves creating a hierarchical model. The difference is that modeling involves creating a model of the behavior of structures and components of aircraft in conditions of uncertainty of input parameters at two levels: macroscopic method, finite element modeling and microscopic methods of quantum mechanics and molecular dynamics, where the first considers the microscopic samples representing the model is geometrically similar to the standard samples used for m is a mechanical test,
which virtual testing methods, molecular dynamics, and the resulting mechanical properties of microscopic samples is used as the missing macroscopic parameters in models of materials for finite element modeling, and the transition from microscopic to macroscopic level modeling and back using the scale invariance of the mechanical parameters and laws.

In our method is not a simple hierarchy of scales, but a more complex hierarchy of laws, this means that to obtain the mechanical parameters of the upper hierarchical level parameters are used, derived from other than mechanical, patterns, approaches (based on megalomania quantum-mechanical interaction), which allow a high degree of accuracy to virtually test. In addition, the uncertainty of the parameters in our case due to the empirical law behavior of materials (material model for finite element analysis.

The method of mathematical and computer modeling, including the creation of a hierarchical model, consider the example of modeling elements of aircraft structures made of α-titanium alloys VT1, VT1-0), as titanium is a classic of aviation material.

Consider as an example the possibility of obtaining modules of elasticity (required parameters for finite element modeling) from molecular dynamics simulation, i.e. simulation at the microscopic level - the methods of quantum mechanics and molecular dynamics, where the first considers the microscopic samples representing the model geometrically similar to the standard samples used for mechanical testing, which virtual testing methods finite element simulation.

Create (generate by computer) sample material in accordance with the experimental values of lattice parameters, the direction of the crystallographic axes, the parameters used interatomic potential (figure 1). This procedure can be performed by any standard method known free packet molecular dynamics simulation (for example, Lampps, NWChem). Then deformiruem. sample programmatically according to specified the program loading (figure 2).
In this case, were stretching along the Z-axis at a given speed. Performed procedure corresponds to the standard macroscopic procedure of the study sample in the gap defined by the existing engineering practices and standards. According to the results of a computer experiment-defined valuesα- radius-vector defining the position of a particle with number α relative initial particle in the reference configuration, which are parameters in the formula

cijkl=12v∗∑α(1aα2d2Φdaα2-1aα3dΦdaα)aαaαaαaα

where cijkl- modulus of rigidity; Φ is used in the model potential; V∗- the volume of the elementary crystal cell of the lattice; andαis the radius-vector that defines the position frequent the hospitals with the number of α relative initial particle in the reference configuration.
In the formula the distance between the atoms is expressed in the form ofrij2=aα2+2aα⋅aα⋅⋅εijand used direct tensor notation for tensor and dyadic multiplication, εkl- Lagrangian deformation volume of the material.

The obtained values are used as input parameters for finite element modeling. It is known that finite element modeling, for example in packages LSDYNA, ANSYS, the material behavior is governed by a set of parameters from which the tensor of elastic modulus (inverse of stiffness) is the main mechanical characteristics.

From the results of a computer experiment (figure 2) also defines a module Poisson (similar to the standard macroscopic experimental determination of this module).

In using scale invariance is the fact that the equations of mechanics do not change their form depending on the chosen system of units and scale length. This allows you to distribute the settings and dependencies obtained for the mechanical system of some size, other sizes.

On microscopica the com layer model body,
geometrically similar to the standard samples used for the macroscopic mechanical tests (figure 3). The number of atoms in a microscopic model of the system on the left coincides with the number of nodes in a macroscopic system (figure 4). Necessary for microscopic simulation parameters (type and lattice parameters, the parameters of the interatomic potential) must coincide with the experimentally defined for this type of material parameters. Microscopic virtual samples are tested by the methods of molecular dynamics, for example made an impact on the sample at a specified rate to a specified value of deformation. From the resulting computer model known from the physics and mechanics of solids dependencies calculated the necessary parameters, for example the tensor modules of elasticity/stiffness ofcijkl=12v∗∑α(1aα2d2Φdaα2-1aα3dΦdaα)aαaαaαaα. Because it is believed that the principle of scale invariance is performed, the effective stresses in the material must be identical. It should be noted that the dimensionless parameters (e.g., Poisson's ratio) do not need further renormalization and dimensional units must lead to macroscopic scale based on the conventional theory of dimensions. For example, if L∗ is the characteristic dimension (e.g. length) of the microscopic sample, L is the same characteristic size of the macroscopic sample (long), all the quantities involved in the calculation of the dependence and has the dimension of length, decrease in the ratio λ=L∗/L.

For example, if the MD simulation is used atomic system of units (AMU / Angstrom / PS), to obtain the macroscopic values of the modulus of elasticity (dimension[E]=[FS]=[Nl2]=[m⋅ls2l2]=[ms2l]should the obtained microscopic value to multiply by the scale factor of 1.66∗107,

where [E] is the dimension of the modulus of elasticity

[F] is the dimension of force,

[S] is the dimension of the square.

Besides finding the missing mechanical properties of materials MT-model allows to investigate the dynamics of the processes of deformation and fracture - see figures show a fairly good agreement of results when predicting the propagation of cracks, and other processes.

The method of mathematical and computer modeling, including the creation of a hierarchical model, wherein the simulation includes creating a model of the behavior of structures and components of aircraft in conditions of uncertainty of input parameters at two levels: macroscopic method, finite element modeling and microscopic methods of quantum mechanics and molecular dynamics, where the first deals with microscopy the mini samples
representing the model geometrically similar to the standard samples used for mechanical testing, which virtual testing methods, molecular dynamics, and the resulting mechanical properties of microscopic samples is used as the missing macroscopic parameters in models of materials for finite element modeling, and the transition from microscopic to macroscopic level modeling and back using the scale invariance of the mechanical parameters and laws.

SUBSTANCE: invention relates to automated information collection, processing and analysis systems, as well as artificial intelligence systems and can be used in designing, testing, studying and improving automated information collection, processing and analysis systems, including special-purpose information-telemetry software systems of space-rocket equipment specimens. A test object is placed in a software system for simulating a group telemetric signal and situations are simulated, the degree of aggregation of which is lower than the aggregating capacity of the test object. Weights and graph edges are adjusted. A multidimensional realisation graph of a decision function is obtained, which is differentially mapped on a plane. Characteristic structures are identified. Situations which cause initiation of peaks and graph edges, which form characteristic structures, are simulated, giving rise to a new multidimensional graph with new characteristic structures on a projection. Iterative readjustment of the realisation graph of the decision function is therefore performed.

EFFECT: detecting system and syntax errors in algorithms of systems and minimisation thereof based on system morphogenesis.

SUBSTANCE: device for simulating mass service systems has an request flow generator, an incoming request counter, a counter of requests denied service, a random time delay unit, a bidirectional counter of busy channels, a bidirectional counter of the length of the queue, a four-input OR element, a counter 6 of serviced requests, a three-input AND element, a five-input AND element, a two-input AND element with inverting inputs, two three-input AND elements with inverting inputs, three four-input AND elements with inverting inputs, a five-input AND element with inverting inputs, an N-input NAND element, where N is equal to the number of bits of the bidirectional counter of busy channels, an N-input NOR element, an M-input NAND element, where M is equal to the number of bits of the bidirectional counter of the length of the queue, an M-input NOR element, an L-input OR element, where L is equal to the number of bits of the bidirectional counter of requests denied service, a flip-flop and a divider.

EFFECT: controlling a real mass service system depending on the laws of distribution of the inflow of requests and laws of distribution of their servicing.

SUBSTANCE: computer system analyses compiled code and potentially optional configuration information for implementing a service and converts the compiled code and configuration information into an abstract service description. The abstract service description can then be converted into code document object model and service configuration information or exported as metadata. A corresponding service runtime can be initiated by calling a service initialisation module included in the abstract service description. The code document object model and configuration information and/or metadata can be transferred to another computer system. The other computer system can use the code document object model and configuration information and/or import the metadata to facilitate initialisation of a compatible channel for information exchange with the service runtime.

EFFECT: minimisation of incompatibility factors between client and service runtimes.

SUBSTANCE: teaching method is realised using an instruction system which includes a numerical series calculator which has a processor with two adder accumulators connected in series. The instruction system has hardware for controlling its operation, as well as data processing hardware, numerical series calculator, data storage memory, data display hardware and hardware for inputting data into the instruction system.

EFFECT: reduced computational load on the student due to automation of numerical series calculation by the instruction system.

SUBSTANCE: invention is related to computer system, which is based on software of single well predictive model (SWPM). The first specific sequence of operations is automatically created, which consists of the first multitude program modules, in response to the first set of user tasks, and the first specific sequence of operations is automatically executed in response to the first set of input data for creation of the first target product, and the second specific sequence of operations is automatically created, which consists of the second multitude program modules, in response to the second set of user tasks, and the second specific sequence of operations is automatically executed in response to the second set of input data for creation of the second target product, in which target product is three-dimensional model of collector response.

EFFECT: provision of low modeling on the basis of single well predictive model, which combines statistic and dynamic measurements with data of completion.

SUBSTANCE: invention relate to the computer simulation of the centering of a cargo aircraft of type "АН-124-100". Technical result consists in increase of accuracy of calculations and visualisation of communication between graphic representation of geometry of a cargo cabin of the plane and the big party of cargoes with numerical representation of the information on the latter, and also acceleration of process of preparation and processing of dimensional-mass parameters of a cargo with the purpose of its loading. The method is based on formation of the database containing data on mass characteristics of the plane of type "АН-124-100", including data about individual mass-centering parameters of planes of type "АН-124-100" depending on onboard number of the plane and about mass-geometrical parameters of cargoes, and the subsequent display of images of the established cargoes on a tablet of a floor of a cargo cabin and current value of centering of the plane in percentage of an average aerodynamic chord.

EFFECT: increasing in the accuracy of the simulation of centering of a cargo aircraft.

FIELD: technology for automatic modeling of system for controlling process, wherein elements of user interface are organized in tree-like structure, reflecting topography of elements in process control system.

SUBSTANCE: each element is assigned to at least one input window, having a set of attributes for setting up and/or monitoring target device, controlled in system for controlling process. Current organization of tree-like structure is recorded as project, and list of all windows, opened during one and the same operation, and also attributes, are recorded as work session, by means of which state of elements is restored during repeated loading of process control system.

FIELD: computer science, possible use for controlling status of various changing objects.

SUBSTANCE: method includes preliminary creation of model of object with division or isolation of object in blocks, each of which is assigned at least one identifier: identifier of position of block in object and identifier of time period, during which block looks remained unchanged; isolation of one additional block during change of object with assignment of two aforementioned identifiers to block; building of model of additional block, selection of block on basis of time period identifiers, included in request, and building of model of object in accordance to identifiers of position of blocks in object.

EFFECT: creation of method for recording and visualization of type of changing object in any time moment, which can be realized using equipment, not having high productiveness and speed of operation.

FIELD: means for calculating cost of project during earlier stages of engineering.

SUBSTANCE: system for estimating cost of project, realized as computer software, has type module for receiving user input, determining type of project, and for forming requirements to project, project module receives requirements for project and compiles a project, including given data, operating characteristics data receives data from calculations and generates parameters of working characteristics, cost module receives data and determines cost, client cost module takes in working characteristics and determines cost of project for client.

SUBSTANCE: invention relates to digital computer engineering and is intended for planning the topology of logic integrated circuits when designing computer systems. The apparatus includes a device for searching for a lower estimate of arrangement in matrix systems with two-way information transmission and a device for planning the topology of logic integrated circuits, comprising a microprocessor, random-access memory, a memory direct access controller, a parallel port, a serial port, a PLD topology planning unit, an adjacency matrix and a circuit matrix of a unit for finding the minimum lower estimate, a search permutation unit, a unit for finding the minimum lower estimate, a unit for searching for the initial value of communication delay.

EFFECT: planning the topology of programmable logic devices (PLD) based on the criterion of minimising the intensity of interaction of processes and data.

SUBSTANCE: device comprises a clock-pulse oscillator (CPO) 1, an enable trigger 2, a trigger of result availability 3, a group of counters 41, 42, …, 4m, a matrix (m×n) of triggers 511, …, 5mn, a matrix (m×n) of groups of the first AND elements 611, …, 6mn, a group of the first summators 71, 72, …, 7n, a group of the first registers 81, 82, …, 8n, a group of the first comparison circuits 91, 92, …, 9n, the second AND element 10, the second summator 11, the second comparison circuit 12, the group of second registers 131, 132, …, 13m, the third register 14, a start inlet 15, an inlet of initial setting of a device 16, a group of the first outlets of a device 171, 172, …, 17m, the second outlet of a device 18, the third outlet of a device 19, a group of the fourth registers 201, 202, …, 20m, a group of the fifth registers 211, 212, …, 21m, a group of the third comparison circuits 221, 222, …, 22m.

EFFECT: increased reliability of a device and increased efficiency of a device.

SUBSTANCE: invention relates to automated drawing means. The method includes identifying a previously drawn object within a grid with a first gridline spacing; determining a dimensional unit of said object; automatically adjusting gridline spacing from the first to the second as a function of the dimensional unit, where the first spacing differs from the second and where some of the steps for identification, determination or automatic adjustment are carried out by a computer processing unit.

EFFECT: high speed of drawing by providing dynamic adaptation of the gridline spacing to the object being drawn at the present moment.

SUBSTANCE: invention relates to methods, devices and computer-readable media for calculating a physical value and numerical analysis. A computer-executed method of calculating a physical value comprises a physical value calculation step of calculating, using a central processing unit, physical values in an analysis domain divided into a plurality of divided domains using a discretised governing equation which uses values not requiring coordinates (Vertex) of vertices of the divided domains and connectivity information (Connectivity) of the vertices and which is derived based on a weighted residual method and a calculation data model in which volumes of the divided domains and characteristic values of boundary surface indicating characteristics of boundary surfaces of adjacent ones of the divided domains are provided as the values not requiring coordinates (Vertex) of vertices of the divided domains and connectivity information (Connectivity) of the vertices. The discretised governing equation and the calculation data model are stored in a storage device.

EFFECT: reduced operating load when forming a calculation data model and low computational load in the resolving process without deterioration of analysis accuracy.

SUBSTANCE: invention relates to drilling simulation device. Portable drilling simulation system comprises master control computer, graphic job computer, flow bean board and blowout preventer board. Said master control computer, graphic job computer, flow bean board and blowout preventer board are interconnected via network and serial ports. Said blowout preventer board comprises control board. Blowout preventer control zone is located at the right side of said control board. Flow bean manifold control zone is located at top part of the right side. High-pressure manifold control zone is located at bottom part of the right side. Flow bean board comprises appropriate control board. Master control computer and graphic job computer incorporate appropriate software.

SUBSTANCE: invention relates to automated aircraft simulation means. The method involves defining a parametric space grid; obtaining a model for calculating dimensional variables for whatever point in the parametric space, where values of said one or more dimensional variables are calculated for the initial group of points using a CFD model; obtaining an initial ROM model from said CFD calculations; selecting a point of the group with the highest deviation between CFD and ROM model results; selecting new points in the parametric space to be added to the group of points; calculating values of dimensional variables for the new points using the CFD and ROM model.

SUBSTANCE: method of determining the permitted building volume based on duration of sun exposure in architectural design involves creating three-dimensional models of existing buildings and a preliminary volume allocated for the new building, determining sectors of the beginning and end of sun exposure at design points, the method being characterised by that it involves first determining sectors of initial sun exposure at design points before erecting the new building, then determining minimum sectors and, based thereon, beam volumes which create the permitted duration of sun exposure at such points, and by subtracting said volumes from the preliminary building volume, the permitted building volume is obtained, wherein the position of minimum sectors of sun exposure inside the initial sectors of sun exposure is optimised to provide the largest permitted building volume.

EFFECT: optimum determination of the largest possible volume of space in which a new building of any shape will provide the minimum required duration of sun exposure at design points of existing buildings and territories.

SUBSTANCE: invention can be used for multiparameter facilities, particularly in control system (CS) structures for designing onboard intelligent systems (OIS) for providing navigation safety. The method involves: generating, at the panel of a control unit for controlling the process of creating an OIS CS, a command to begin designing the OIS CS structure and transmitting said command to a conceptual unit, generating tasks, functions and methods of controlling the OIS, generating versions of the functional and organisational structure of the OIS CS, optimising versions of the composition and structure of the OIS CS according to a given criterion, simulating operating modes of the OIS CS based on a service repository, principles for processing information in a multiprocessor computing environment and catastrophe theory techniques, checking conformity of parameters of the composition and structure of the OIS CS to given criteria and input characteristics, in case of nonconformity, correcting input characteristics of the OIS CS and repeating the design process, in case of conformity, preparing specification documents for the OIS CS.

EFFECT: high efficiency of designing an OIS CS, providing navigation safety for dynamic marine objects, operating in real time in a complex dynamic environment based on measurement data, a structured knowledge base and mathematical modelling techniques using a dynamic catastrophe model.

SUBSTANCE: operating efficiency of a vehicle system is determined by creating a computer model of the vehicle, which provides the required confidence level, and performing numerical simulation of processes occurring in the vehicle during different accident scenarios.

EFFECT: checking operating efficiency of a system at the development stage without full-scale testing.

SUBSTANCE: invention relates to stringer, method of developing stringer model with the help of computer, aerospace device and aircraft. Said stringer comprises base with first surface and second surface located opposite the first one, and rib with third and fourth surfaces. Stringer has L-like cross-section over its length and geometry varying along the part of its length with distance increasing along its length. Geometry variation represents a shift of said first surface toward second surface and fourth and third surfaces. Cross-section features, in fact, constant distance measured over cross-section surface between the points whereat cross-section intersects with first and second lines for all cross-sections along the part of its length. Proposed method of developing stringer model with the help of computer comprises preparing first data whereat stringer model base geometry is defined and distance from the base to imaginary plane varying along stringer length. Besides it comprises generation of second data whereat stringer model rib is defined including generation of local changes in rib geometry. Said first and second data are used for generation of stringer model. Method of making said elongated comprises making mould, placing composite material layers therein, and curing said layers.

SUBSTANCE: test bench comprises device to apply distributed loads to object under test composed by outer limiting shell with lengthwise and crosswise ribs. The latter makes cells to accommodate inflatable resilient bags connected with pressure gages and gas variable pressure feed system, resilient edges being arranged along edges of said cells. Resilient edges have bearing part attached to said ribs, and lug part pressed to tested object by inflatable bags. Said cells have transducer of displacements at ribs, manhole in limiting shell and are equipped with extra gas variable pressure transducer. Said gas variable pressure feed system relieves pressure in bag at pressure drop rate in opposite cell. Height of bearing part and width of lug part of the edge and its thickness are defined experimentally.